Satellite despun control method based on geomagnetic measurement

A satellite and derotation technology, applied in space navigation equipment, space navigation vehicles, space navigation equipment, etc., can solve problems such as difficult to guarantee the effectiveness of gyroscope fault judgment, unstable output of optical sensors, etc.

Active Publication Date: 2020-01-10
BEIJING GUODIAN GAOKE TECH CO LTD
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Problems solved by technology

The existing satellites are basically equipped with inertial attitude sensors (gyroscopes). The damping controller using gyroscopes is relatively simple due to the three-axis decoupling, and is easy to implement in engineering. The optical sensor of the track time has no output or the output is unstable temporarily. Without the output comparison of other sensors, the effectiveness of the fault judgment of the gyro is difficult to guarantee.

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  • Satellite despun control method based on geomagnetic measurement
  • Satellite despun control method based on geomagnetic measurement
  • Satellite despun control method based on geomagnetic measurement

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Embodiment Construction

[0045] Refer below figure 1 The specific implementation and working principle of the satellite derotation control method based on geomagnetic measurement in the present invention are described in detail.

[0046] like figure 1 As shown, the satellite derotation control method based on geomagnetic measurement provided by the present invention comprises the following steps:

[0047] S100: Establish a satellite attitude matrix according to the coordinates of the magnetic induction intensity of the magnetic field where the satellite is located in the geocentric coordinate system and the transformation matrix;

[0048] In this step, the magnetic induction intensity of the geomagnetic field at the position of the satellite is assumed to be The unit is Wb / m 2 , and its coordinates in the geocentric coordinate system are [B x ,B y ,B z ] T , which can be calculated from the magnetic induction intensity, magnetic declination and magnetic inclination given by the international g...

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Abstract

The invention provides a satellite despun control method based on geomagnetic measurement. The method includes the following steps of establishing a satellite attitude matrix according to coordinatesand a transfer matrix of the magnetic induction intensity of a magnetic field at the location of a satellite in a geocentric coordinate system, establishing a calculation matrix of the variation of the magnetic induction intensity relative to the attitude angular velocity of the satellite according to the satellite attitude matrix, measuring the variation of the magnetic induction intensity, calculating the three-axis angular velocity of the satellite according to the variation and the calculation matrix, and performing despun control on the satellite according to the three-axis angular velocity. Only by measuring the variation of the induction intensity of the magnetic field as the input of a controller, the satellite despun aim can be realized, and the method is simple and high in reliability.

Description

technical field [0001] The invention relates to the technical field of satellite attitude control, in particular to a satellite derotation control method based on geomagnetic measurement. Background technique [0002] When the satellite is just in orbit, due to various reasons during separation, the initial angular velocity of the satellite may be relatively large, reaching the order of 1-5° / s. When the satellite recovers from the failure, its angular velocity may be even greater, even When it reaches 10° / s, the first task of the satellite is to damp the initial angular velocity of the satellite. The existing satellites are basically equipped with inertial attitude sensors (gyroscopes). The damping controller using gyroscopes is relatively simple due to the three-axis decoupling, and is easy to implement in engineering. The optical sensor of the track time has no output or the output is unstable temporarily. Without the output comparison of other sensors, it is difficult to...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/32
CPCB64G1/32
Inventor 朱莲枝
Owner BEIJING GUODIAN GAOKE TECH CO LTD
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